航空工程进展
航空工程進展
항공공정진전
ADVANCES IN AERONAUTICAL SCIENCE AND ENGINEERING
2012年
1期
39-43
,共5页
NACA0012半模机翼%NACA64-210半模机翼%升力特性%测力实验%静态%振动
NACA0012半模機翼%NACA64-210半模機翼%升力特性%測力實驗%靜態%振動
NACA0012반모궤익%NACA64-210반모궤익%승력특성%측력실험%정태%진동
NACA0012 half-model%NACA64-210 half-model%lift characteristics%force measurement%steady state%vibrating
飞行器机模型振动是影响其风洞实验数据可靠性的主要因素之一。为此,通过专门研制的半模振动模型,采用对称翼型NACA0012和层流翼型NACA64-210两种半模机翼进行了低速风洞振动实验。选取五种激振方式,用直接测力法得到模型在静态和不同激振方式下升力特性变化曲线,研究了振动频率、自然转捩和固定转捩、数据采集方式等参数对机翼气动特性测量结果的影响。结果表明：振动对半模机翼气动特性的影响程度因不同翼型构型、不同采集方式和翼面不同流动模式等而产生不同效果。结论对提高飞机模型风洞实验大迎角振动情况下的测量精准度有参考价值。
飛行器機模型振動是影響其風洞實驗數據可靠性的主要因素之一。為此,通過專門研製的半模振動模型,採用對稱翼型NACA0012和層流翼型NACA64-210兩種半模機翼進行瞭低速風洞振動實驗。選取五種激振方式,用直接測力法得到模型在靜態和不同激振方式下升力特性變化麯線,研究瞭振動頻率、自然轉捩和固定轉捩、數據採集方式等參數對機翼氣動特性測量結果的影響。結果錶明：振動對半模機翼氣動特性的影響程度因不同翼型構型、不同採集方式和翼麵不同流動模式等而產生不同效果。結論對提高飛機模型風洞實驗大迎角振動情況下的測量精準度有參攷價值。
비행기궤모형진동시영향기풍동실험수거가고성적주요인소지일。위차,통과전문연제적반모진동모형,채용대칭익형NACA0012화층류익형NACA64-210량충반모궤익진행료저속풍동진동실험。선취오충격진방식,용직접측역법득도모형재정태화불동격진방식하승력특성변화곡선,연구료진동빈솔、자연전렬화고정전렬、수거채집방식등삼수대궤익기동특성측량결과적영향。결과표명：진동대반모궤익기동특성적영향정도인불동익형구형、불동채집방식화익면불동류동모식등이산생불동효과。결론대제고비궤모형풍동실험대영각진동정황하적측량정준도유삼고개치。
Vibration of an air-vehicle model is one of factors that affect the reliability of test data in wind tunnel. Therefore a vibration test of half-model wing respectively with NACA0012 aerofoil and NACA64-210 aerofoil conducted in NF-3 wind tunnel is presented. Through the specially designed the elastic model with five exciting methods, the aerodynamic characteristics are investigated and analyzed by directly measuring force using a box balance. The affection factors, such as frequency, Reynolds number, boundary layer transition and data acquisi- tion mode, are investigated. It is shown that the lift aerodynamic characteristics of the half-model are affected by some factors,such as the aerofoil contour, the modes of data acquisition and boundary layer transition, etc. The conclusion is of guidance value on improvement of wind tunnel model test accuracy with vibration at larger angle of attack.
